Hybrid rotor arrangement for a gas turbine engine architecture

Abstract

Structures for hybrid rotor architectures in gas turbine engines, and an assembly method thereof, are described. A gas turbine engine includes a plurality of compressor stages. The gas turbine engine includes a plurality of turbine stages. The gas turbine engine includes a joint between a first compressor stage of the plurality of compressor stages and a first turbine stage of the plurality of turbine stages. The gas turbine engine includes a cone arm coupled to the first compressor stage and the first turbine stage via the joint. The gas turbine engine includes a tie rod threadedly coupled to an end of the cone arm opposite the plurality of compressor stages, the tie rod extending at least a length of the plurality of compressor stages.

Dependencies are inferred from the claim text.